Unmanned aerial vehicle with integrated paintball projectile system and method for use

Abstract

An unmanned quadcopter aircraft system integrated with a pneumatic paintball projectile launching mechanism for recreational and training applications. The system includes a compressed gas powered single-shot paintball launcher with gravity-fed ammunition hopper, mechanical counterweight recoil compensation, and multiple electronic safety systems. GPS-based geofencing prevents firing in restricted zones, while altitude sensors prevent firing above predetermined heights. The flight control system automatically reduces aircraft speed and altitude limits when the projectile system is armed. A ground control system integrates standard flight controls with firing controls, safety indicators, and emergency stop capability. An alternative embodiment allows a used to adjust the elevation of the firing system while maintaining the orientation of the drone in space and also allowing recoil compensation. The system enables aerial paintball gaming and training scenarios while maintaining safety through redundant control systems and automatic parameter limiting.

I claim: 
     
         1 . An unmanned aerial vehicle system, comprising:
 a commercially available drone comprising:   a quadcopter aircraft frame supporting four rotor assemblies with associated motors and flight control systems as known in the art;   standard UAV flight control processors, GPS receivers, and altitude sensors;   a pneumatic projectile launching subsystem (PPLS) mounted to the aircraft frame, the subsystem comprising:
 an ammunition storage hopper; 
 an ammunition feed subsystem; 
 a compressed gas supply; 
 a feed tube; 
 a firing chamber; 
 a pressure regulator; 
 a solenoid valve; 
 a gas tube; 
 a barrel; and 
 an orifice connecting the feed tube to the firing chamber; and 
   a gas flow control subsystem preventing backward gas flow through the ammunition feed subsystem, the gas flow control subsystem, comprising a projectile deformation sealing mechanism wherein projectiles undergo controlled elastic deformation under firing pressures to reduce gas leakage clearance around the projectile circumference;   a counterweight recoil compensation subsystem mechanically coupled to the PPLS using mass of system components as counterweight;   an electronic control subsystem comprising a firing control circuit configured to interface with the standard UAV flight control processors, GPS receivers, and altitude sensors;   a safety control circuit configured to prevent projectile firing based on GPS position and altitude data received from the standard UAV flight control subsystems; and a ground control subsystem.   
     
     
         2 . The system of  claim 1 , further comprising:
 a soft, split-diaphragm feed gate and O-ring seal located upstream from the firing chamber; and   a relief hole upstream of the feed gate.   
     
     
         3 . The system of  claim 1 , wherein the counterweight recoil compensation subsystem comprises a moveable mass attached to a second arm that displaces in opposition to projectile firing recoil forces exerted through a first arm, said first and second arms being fixedly attached to each other at a bearing surrounding an axle. 
     
     
         4 . The system of  claim 3 , wherein the counterweight recoil compensation subsystem comprises the compressed gas supply as the counterweight mass positioned on an opposite side of the drone center of gravity from the projectile launching subsystem. 
     
     
         5 . The system of  claim 1 , wherein the safety control circuit comprises a geofencing module that prevents firing when the drone is within predetermined restricted zones. 
     
     
         6 . The system of  claim 1 , wherein the safety control circuit prevents firing when the drone altitude exceeds a predetermined maximum firing altitude. 
     
     
         7 . The system of  claim 6 , wherein the predetermined maximum firing altitude is 50 feet above ground level. 
     
     
         8 . The system of  claim 1 , wherein the electronic control subsystem automatically reduces maximum aircraft speed when the PPLS is armed. 
     
     
         9 . The system of  claim 1 , wherein the ammunition storage hopper has a capacity of twelve paintballs and utilizes gravity-fed delivery to the firing chamber. 
     
     
         10 . The system of  claim 1 , further comprising a ground control subsystem with integrated firing controls, safety indicators, and emergency stop capability. 
     
     
         11 . The system of  claim 1 , also comprising an elevation control subsystem comprising:
 a pivot bearing assembly providing a horizontal rotation axis perpendicular to the drone longitudinal axis;   a servo arm connected between the servo motor output shaft and the pneumatic projectile launching subsystem;   position feedback sensors providing elevation angle information; and   mechanical stops limiting elevation travel to prevent rotation beyond 90 degrees.   
     
     
         12 . The system of  claim 3 , wherein the counterweight recoil compensation subsystem also comprises:
 a servomotor connected to a bearing;   a linkage connecting the servomotor to an actuator through an actuator linkage; and   wherein the servomotor adjusts the elevation of the PPLS and simultaneously adjusts the position of the counterweight mass on the second arm to maintain static stability.   
     
     
         13 . The system of  claim 11 , wherein control software and hardware:
 provide pulse-width modulation control signals to the servomotor;   obtain position data from rotary encoders or potentiometers attached to the bearing and the second arm; and   prevent elevation adjustment during firing sequences.   
     
     
         14 . A method of operating a drone with an integrated projectile system safely, comprising:
 allowing gravity to cause a paintball to drop from an ammunition hopper through a feed tube into a firing chamber fixedly connected to a barrel of a pneumatic projectile launching subsystem;   providing a transition orifice having an internal diameter larger than the nominal projectile diameter;   allowing controlled elastic deformation of projectiles under firing pressure to reduce gas leakage clearance in the transition orifice;   positioning a one-way check valve in the ammunition feed path upstream from the firing chamber;   configuring the check valve with a cracking pressure of 2-4 PSI for forward projectile flow and sealing capability above 150 PSI for reverse gas flow; and   integrating both sealing mechanisms to limit total backward gas leakage to less than 10% of forward gas flow;   receiving GPS position data and altitude data from the drone;   comparing the GPS position data against a database of restricted firing zones;   comparing the altitude data against a maximum firing altitude threshold;   enabling projectile firing only when the drone is outside restricted zones and below the maximum firing altitude;   automatically modifying flight parameters to reduce maximum speed and altitude when the PPLS is armed;   receiving an electrical signal transmitted wirelessly from a ground control system;   causing the electrical signal to activate a solenoid connected to a valve;   causing the valve to release gas from a compressed gas cartridge;   the increased gas pressure in the firing chamber causing the paintball to be expelled from the barrel.   
     
     
         15 . The method of  claim 14 , further comprising neutralizing firing recoil forces using a mechanical counterweight subsystem to maintain aircraft stability, wherein the counterweight subsystem operates in a vertical plane with recoil forces directed upward and compensation forces directed downward. 
     
     
         16 . The method of  claim 14 , wherein the maximum firing altitude threshold is 50 feet above ground level. 
     
     
         17 . The method of  claim 14 , further comprising providing visual and audio data feedback to an operator on a ground control system indicating armed/disarmed status and safety subsystem states. 
     
     
         18 . The method of  claim 14 , further comprising an elevation-controlled projectile subsystem comprising:
 commanding a servomotor to position the pneumatic projectile launching subsystem at the calculated elevation angle;   automatically positioning the counterweight assembly to provide optimal recoil compensation for the selected elevation angle;   verifying elevation angle is within safety parameters based on aircraft altitude and GPS position;   enabling projectile firing only when elevation positioning and safety checks are complete; and   returning the elevation-controlled projectile subsystem to a statically stable position after firing sequence completion.